Aeroplane



Jan. 20; 1925-, 1,523,3@6'

- F. BAER A AEROPLANE Filed April 15, 1925 2 Sheets-Sheet l Patented Jan. ze, 1925.

. u iran FRIEDERYICK BAER, OF NEW' YORK, N. Y. l

To all whom it 17mg/ concern.' Be it known that: I, FRIEDERICL; BAER a citizen of Switzerland, residing at NewL York, in the county of New York and State of New York, have invented certainv new and useful Improvements in Aeroplanes, of which the following is a specification.

This invention relates .to certain new and useful improvements in aeroplanes, and it has for its objects among others to provide a special construction to take the place of all control wires in the. event of disability, and to enable one to maintain perfect control of the aeroplane so that he may make a turn to theright or to the left, or take or prevent a nose-dive as may be desired, or toloop the loop, as well as to shorten the turn of the device or the loop.

It has for a further object to provide for l'ifting the weight of themotor so as to prevent the plane from striking the ground with great force, and also saving the device from tipping over on its nose as when forced to make a landing on avery bad field. On a smooth'kield the control blades Vmay be so turned as to reduce the speed of the plane. The two blades are mounted lfor operation and control independent of each other, or-in unison, and are so stable and strong *as to be absolutely fool-proof in case of broken wires. Should both control wires break atthe same time, by use of both hands one can change the controls from one position to another, and so on back and forth the same as if one was using a control stick. Inactual flying the control ywill help to take the weight ott of the motor if placed in neutralposition and relieve the other` control of heavy strain.

' The present invention has for a further object to provide a light. yet strong and durable blade having its shaft so embodied therein as to give great rigidity combined with lightness, and also a bearing for the shaft, readily attachable to the engine bed and having roller bearings and an .end thrust bearing. The shaft is formed with integral means for the attachment of a control member. t

-In my control I dispense with the employment of all wires and provide means of sufficient strength to withstand all strain. My contro-l means may be employed for the same purpose even when the control Wires or the flippers are not broken.

Other objects and advantages of thelincient strength to withstand all PLANE.

Application led April 13, 1923. Serial No. 631,801.

vention will hereinafter appear and the novel features thereof will be particularly pointed out in the appended claims.

-The invention, in its preferred form, is clearly illustrated in the accompanying drawings, which, with the numerals of reference marked thereon, form a part of this specification. and in which- Figure l is a diagrammatic side elevation showing my vinvention applied to an aeroplane.

Figure 2 is a top'plan.

,Figure 3 is a perspective View of my control mechanism.

Figure 4 is a view partly in section and partly in elevation showing one of my improved bla-des or wings and the bearing for its shaft.

Figure 5 is al view looking down upon Figure 4, with the parts of the bearing in plan instead of in section.

Figurez is a longitudinal section'through one of the blades or Wings` taken substantially centrally and flatwise thereof.

i Figure 7 is an end view looking in the direction of the arrow 7 in Figure 4.

Like numerals of reference indicate like parts throughout the different views.

The aeroplane vis indicated generally by the numeral l, see Figures 1 and 2, and may be of any well-known or approved type, and hence will not be described in detail except in so far as pertains te my present invention, and for the same reasonparts thereof not entering into or forming a part" of, or-necessary to, ia proper understanding of my present invention have not been illustrated. a

2 is the propeller, it being understood that "the propeller, the planes, the ailerons andv the other elements of the aeroplane are as usual in any of thev well-known types.

My improvement pertains to means to be" the use of wires and employ rods''of su- I possibility of derangement or disability from this source. For t is purpose I employ two blades or wings Sand 4', which are made strong and durable so as to withstand the strain and pressure to which they are likely to be subjected in flying.

Referring to Figures 4.- 5, 6 and 7 5 designates the shaft of the blade or wing, the

body 6 of which is` formed preferably of aluminum, being of the flattened oval shape,

seen in Figure 7, being rounded upon its 1 0,as seen clearly in Figures 5 and 6. rLhis l ings 11 and 14 is an arm 21, the

-of which is bifurcated, as seen at 22, or

flattened pointed portion of the shaft is molded or cast within the aluminum body 6 with the alternately oppositely disposed portions 10` extended fiatwise toward the opposite tapered edges 7 of the'blade or wing, as seenl best in Figures 5 and 6. This makes a blade that is light, yet strong and durable and one that is rigid and practically homogeneous with its shaft.

As before stated, there are two ofthese blades or wings, one upon each side, near the front, as seen in Figure 2, the shaft 5` of each being mounted most substantially in a bearing 11 supported in the arms 12 and 13, see Figures 5 and 2, and in a further bearing 14 rigidly secured to the plate 15 as by bolts, screws or the like 16, which plate 15, in turn, is Adesigned toV be firmly secured to the engine bed, as by bolts, see Fi re 1.

uitable ball bearings 18 and 19 are pro-`v vided for the shaft in these bearings', as seen in Figure 4, and suitable oil cups 20 are provided, as seen in Figures 4, 5 and 7 18u is a ball in the bearing 14 to take the end thrust of the shaft 5.

Rising from the shaft 5 between the bear# outer end otherwise adapted tohave connected there- -with a rod 23, see Figures 1, 2 and 3. Each of these rods is provided with an upward bend 24 adjacent its connection with the shaft and arm 21, as seen in Figures 1 and '3, and the arm 13 is provided `with 'a bend 25, as seen in Figures 2 and 5, so as to readily permit of thel requisite movement of the its rod, so as to allow the blade a substantially vertical plane. 'f The position `of the planes 3 levers 26 and 27 mounted upon a pivot 28 and accessible tothe pilot in the fuselage, as

seen in Figure1, .the rods 23 extending conver ently from theirpoints of connec? tion with the arms 21, as seen in Figures 2 and 3, and connected at their rear ends,`

as ,at 29, -with the lower ends of the levers v 26 and 27, seen in Figure 3. The upper ends'ofthese members straddle an arcuate member 30 Lfixedly secured in place and provided with a rack or toothed member 31 with which engage' suitable pawls carried without departing from the and i is aetermined and controlled by means of two of the levers.

In use, my'improved mechanism-may be employed whether the ailerons or their control wires are broken or not, and if not broken, will shorten the turn of the machine. If the aileron wires are broken, by pushing one of my control levers forward and the otherI backward it will cause the machine to make a turn to-the left. If the control levers are moved in the' reverse direction the result will lbe a turn to the right.

In preventing a nose-dive, the two concase my control blades take the place of the broken flippers. To make a nose-dive the control levers are moved in thel opposite direction. l

In making a loop-the-loop, if my improved control device is used in connection with the ordinary flippers one can make the loop-theloop in almost the length of the machine.

In making a landing on a smooth field, by placing the control levers straight only about `the time the machine strikes the ground the speed of the plane will be materially reduced.

In making a` forced landing, as upon va very bad field, by putting the control levers half way from' neutral to the front, the blades will lift the heavy weight of the motor and thus prevent the plane from striking the ground with much force, and saves Athe machine from tipping over on its nose. The controlling blades or wings 3 and 4 may be actuatedin unison, or independently of each other.

Modifications in detail may be resorted to irit of the introl levers are moved to the front; in this'v vention or sacrificing any of its advantages.

1. In an aeroplane, a blade consisting of an aluminum body of flattened form, and a shaft therefor having 'laterally extended portions molded within the aluminum body, the end of the shaft extended to and forming the poin't of the blade.

.2. In an aeroplane, a an aluminum body of flattened form, and a shaft therefor having laterally extended portions' molded within the aluminum body, saidbody being tional form w1th its end extended to and. forming the point of the blade.

an aluminum body of flattened form, and a shaft therefor having laterally extended portions moldedwithin the aluminum body, said body being ofelongated oval cross-seotional form and tapered both longitudinally and transversely. the end of the shaft extended to andv forming the point of the blade.

4. In an aeroplane, a blade conslstmg of blade consistingl ofof elongated oval cross-sec 3.In an aeroplane, a blade consisting of an aluminum body of iattened form, and a shaft therefor having laterally extended portions molded within the aluminum body, said shaft having a rigid lateral arm.

5. In an aeroplane, a blade consisting of anv aluminum body of flattened form, a shaft thereforhaving laterally extended portions molded within the aluminum body, said shaft having a rigid lateral arm, and a bearing for said shaft provided with a ball to receive the end thrust of-the shaft.

6. In an aeroplane, an air-foil control shaft bearing having arms with means for the attachment thereof to the engine bed` and means to takethe end thrust of vthe shaft.

7. In an aeroplane, a shaft bearing having arms ,with means for the attachment thereof tothe engine bed, and means to take the end thrust of the shaft, said bearing comprising arms extended from the base and one of which is provided with an inward bend.

8. In an aeroplane, a shaft bearing having arms with means for the attachment thereof to the engine bed, means to take the end thrust of the shaft, said bearing comprising arms extended from the base and one of which is provided with an inward bend, and a shaft having a lateral member for attachment to an arm for actuating the shaft to vary the inclination of its blade.

9. yIn an aeroplane, a shaft bearing having arms with means for the attachment thereof to the engine bed, means totake'the end thrust of the shaft, said bearing comprising arms extended from the base and one of which is provided with an inward bend, a shaft having a lateral member for attachment to an arm for actuating the shaft to vary the inclination of its blade, and a rigid arm connected to said member.

In testimony whereof I affix my signature.

FRIEDERICK BAER. 

